System and method for thermal control in a gas turbine engine
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United States of America Patent
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Apr 14, 2015
Grant Date -
Jun 20, 2013
app pub date -
Dec 16, 2011
filing date -
Dec 16, 2011
priority date (Note) -
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Abstract
A system includes a gas turbine engine that includes a compressor section configured to generate compressed air and a combustor coupled to the compressor section. The combustor is configured to combust a first mixture comprising the compressed air and a first fuel to generate a first combustion gas. The gas turbine engine also includes a turbine section coupled to the combustor. The turbine section is configured to expand the first combustion gas to generate an exhaust gas. The gas turbine engine also includes a boiler coupled to the turbine section. The boiler is configured to combust a second mixture comprising a portion of the first combustion gas and a second fuel to generate a second combustion gas that is routed to the turbine section. In addition, the boiler generates a first steam from heat exchange with the second combustion gas.
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